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Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
The primary objective of this project was to develop Gas-Fed Pulsed Plasma Thrusters (GF-PPT) that can be used with water vapor or hydrazine as fuel, with vapor pressures of less than 1 Torr necessary to operate the thruster. This propulsion technology can be used to perform orbit phase changes or plane (inclination) changes for near and intermediate-earth orbit satellites. GF-PPT technology is particularly suited for large DELTA-V, in-plane, orbit phase changes. This technology can therefore complement resistojet technology and allow rapid constellation redeployment to insure prompt satellite coverage of conflicts at any location on the surface of the earth with a constellation of satellites optimized for minimum size and cost. This report discusses GF-PPT thruster performance scaling, as well as hardware and power electronics that were developed in this project.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
The primary objective of this project was to develop Gas-Fed Pulsed Plasma Thrusters (GF-PPT) that can be used with water vapor or hydrazine as fuel, with vapor pressures of less than 1 Torr necessary to operate the thruster. This propulsion technology can be used to perform orbit phase changes or plane (inclination) changes for near and intermediate-earth orbit satellites. GF-PPT technology is particularly suited for large DELTA-V, in-plane, orbit phase changes. This technology can therefore complement resistojet technology and allow rapid constellation redeployment to insure prompt satellite coverage of conflicts at any location on the surface of the earth with a constellation of satellites optimized for minimum size and cost. This report discusses GF-PPT thruster performance scaling, as well as hardware and power electronics that were developed in this project.
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781725012127 Category : Languages : en Pages : 28
Book Description
Pulsed plasma thrusters are currently planned on two small satellite missions and proposed for a third. In these missions, the pulsed plasma thruster's unique characteristics will be used variously to provide propulsive attitude control, orbit raising, translation, and precision positioning. Pulsed plasma thrusters are attractive for small satellite applications because they are essentially stand alone devices which eliminate the need for toxic and/or distributed propellant systems. Pulsed plasma thrusters also operate at low power and over a wide power range without loss of performance. As part of the technical development required for the noted missions, an experimental program to optimize performance with respect to electrode configuration was undertaken. One of the planned missions will use pulsed plasma thrusters for orbit raising requiring relatively high thrust and previously tested configurations did not provide this. Also, higher capacitor energies were tested than previously tried for this mission. Multiple configurations were tested and a final configuration was selected for flight hardware development. This paper describes the results of the electrode optimization in detail. Arrington, Lynn A. and Haag, Tom W. and Pencil, Eric J. and Meckel, Nicole J. Glenn Research Center NASA/TM-97-206305, E-11002, NAS 1.15:206305, IEPC-97-127 NAS3-27186; RTOP 632-1B-1B...
Author: Publisher: ISBN: Category : Languages : en Pages : 11
Book Description
The USAF Research Laboratory's (AFRL) Electric Propulsion Group is developing an Advanced pulsed-plasma thruster (PPT) technology demonstration for small satellites. The initial flight opportunity was on MightySat 11.2 - a satellite bus specifically designed to advance AFRL-developed technologies and serve as a risk reduction mission for systems required for TechSat 21. This experiment will demonstrate a high performance PPT, making it a viable thruster for various applications such as orbit raising and initiating and maintaining clusters of small satellites. The experiment will also be the first flight of a new micro-propulsion thruster - a miniaturized version of the PPT, known as the micro-PPT (%-PPT). The u-PPT is ideal for very precise attitude control and pointing, formation flying, and for primary propulsion on microsatellites. A novel on-board diagnostic package will be used to assess the contamination of optical and thermal control surfaces as a result of firing the PPTs. Ground-based observations will also be conducted to assess the on-orbit performance and possible communication impacts of the thruster firings.
Author: Robert J. Vondra Publisher: ISBN: Category : Languages : en Pages : 10
Book Description
A solid fuel pulsed plasma thruster (PPT) has been designed, built and flight qualified for the LES-8/9 program (due to be launched in March 1975). The satellite attitude control system will contain six PPTs for orbit acquisition, east-west stationkeeping, three-axis attitude control and station changes. Each thruster has fuel for 2650 lb-s total impulse and at 25 w generates 69 micropounds thrust at 1100 s specific impulse. A prototype thruster has passed flight qualification shock and vibration tests and operational lifetime. (Modified author abstract).
Author: Fernando Mier Hicks Publisher: ISBN: Category : Languages : en Pages : 189
Book Description
Electrospray thrusters are an attractive technology for small satellite propulsion. A thorough study of the spacecraft charging and attitude control performance of electrospray thrusters acting on a small satellite is presented. The experimental portion of the study employs a new type of magnetically levitated testbed to measure thrust, characterize spacecraft charging phenomena, and demonstrate precision attitude control maneuvers. The testbed magnetically levitates a mockup-satellite in vacuum conditions. The satellite carries thrusters, batteries, radio, and high voltage thruster electronics. The magnetic levitation and high vacuum provide a zero-friction environment for the thrusters to actuate. The thrusters are placed on the satellite in such a way to produce a net torque when fired. The thrusters are fired and the corresponding rotational movement of the satellite is analyzed to calculate thrust. The uncertainty of the thrust measurement is estimated to be ±0.35 [mu]tN (3[sigma]). Theoretical and experimental methods were developed to investigate the spacecraft charging characteristics anticipated to be observed on spacecraft during the operation of electrospray thrusters. These devices can produce positively and negatively charged ion-beams. An electrical model of this configuration was created to predict the charging properties of electrically isolated systems. This model simulates a bipolar electrospray thruster system. Experiments were conducted on the magnetic levitation testbed. The results from the experimental tests demonstrate that neutralization with heavy ionic species is indeed possible. The thrusters are able to fire in a bipolar configuration for long periods of time inducing bounded spacecraft charging in the range from -400V to +600V when emitting currents of about 20 [mu]A. It was found that the presence of low-energy ions produced by the fragmentation of large clusters and the external space plasma play a significant role in the neutralization characteristics. This electrical model was verified by reproducing the experimental results, thus validating its use to estimate bulk spacecraft charging properties. Electrospray thrusters are capable of producing impulse bits in the 10-6 N-s or lower, depending on the configuration. These characteristics have the potential to allow for long term pointing in the arcsecond range or better with practically no jitter. Experimental work is performed on the magnetic levitation testbed to demonstrate the actuation characteristics under non-optimal control. It is found that subject to a noisy attitude sensor and external perturbations, electrospray thrusters are capable of producing pointing accuracies of 22 arcseconds 3[sigma] error during 10 hours on a platform similar in size and mass to a 1U CubeSat. The implementation of such capabilities could complement or eliminate the need of reaction wheels and magnetorquers, especially in missions beyond low earth orbit, while including propulsive capabilities for additional maneuverability in technology development or scientific missions.
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Author: National Aeronautics and Space Administration (NASA)
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Author: Robert J. Vondra
Author: Arturo Valdes
Author: Michael Matthew Micci
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Author: Fernando Mier Hicks